Abstract
In a recent note a method was developed for calculating the reduction in average lift of a cascade aerofoil due to trailing vortices, neglecting the interference due to blockage and stream curvature. Using the numerical values (for a rectangular aerofoil in an unstaggered cascade of finite wings) of the coefficients in the series for the circulation distribution obtained from the Liverpool University DEUCE programme referred to in the previous note, the effect of interference on the spanwise lift distribution has been studied. The analysis has been extended to predict the lift-induced drag ratio of a finite wing in a cascade.
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